Considering a wing section shown below. The leading and trailing edge spars are made with channel section, which have a wall thickness of $2\mathrm{.}5$ mm $,$ a web depth of $125$ mm $.$ The "top hat" stiffeners each have a cross$-$sectional area of $\backslash (50\backslash$mathrm$\{$~mm$\}^\{2\}\backslash )$ where the top and bottom skins are each $2$ mm thick.

Idealize the wing sect$$on into an arrangement or a$$rect stress carry$$ng dooms and snear stress only carrying skins $($see below$)$ where the outer "top hat" stiffeners are each $400$ mm either side of the vertical axis of symmetric. If the section is subject to a vertical shear force through its shear center, $\backslash (\backslash$mathrm$\{$Sy$\}=1500\backslash$mathrm$\{$~N$\}\backslash ).$ Calculate the distribution of shear flow around the section.

Hint: you can refer to Example $20\mathrm{.}4$ to check the boom area, and Example $20\mathrm{.}6$ for shear flow distribution calculation.